边界层对可调节进气道性能的影响

摘要

Abstract:Results of experimental researches of an adjustable three-dimensional inlet in the blow down wind tunnel at Mach numbers from 2 to 6 and unit Reynolds numbers from 0.8× 107up to 6.0× 107 1/m are presented.Influence of swept-forward and swept-back leading edges of the sidewalls and the boundary layer before the channel entrance of the inlet have been investigated.Pressure distribution in channel,mass flow rate and total pressure recovery were determined.Conditions of the inlet start depending on Mach number and flow conditions have been determined.It was shown that the boundary layer exerts determining influence on structure of flow and on the performances of the model inlet.Relatively simple scheme of adjustment of the inlet allows expanding a range of its steady operation.%给出了马赫数2～6、单位雷诺数(0.8～6.0)×107/m时下吹式风洞中可调节三维进气道的试验研究结果.研究了前缘前掠和后掠方案以及进气道入口前边界层的影响.测量了内流道内的压力分布、质量流量和总压恢复系数；确定了进气道启动与马赫数和流动工况的关系.研究结果表明:边界层对流场结构和模型进气道的性能有着决定性影响,相对简单的进气道调节方案可以增大其稳定运行范围.